Improved slide session border controlling and parallel multi-actuator servo loading for high energy loading process of trailing edge flap in aircraft high density energy systems

The flap is an important part of the aircraft structure with high density energy systems, which directly affects the flight performance of aircraft if it gets stuck or disturbed during a powerful control process. Thus, it is difficult to simulate the flap load during flexure and ensure load accuracy during application. To solve this difficulty, this paper proposes improved slide session border controlling (SBC) and parallel multi-actuator servo loading methods for trailing edge flap of aircraft high density energy systems. Also, an optimized efficient follow-up loading test scheme is constructed with improved dual actuator servo loading based on "position control + force control". Flap function tests are realized by constructing a special multi-channel coordinated load control system. In the variable displacement experiment, the calculated displacement value has the same change trend as the static test and the resulting curve is linear. In the principal strain variation experiment, the principal strain variation linearity is standard in the loading range of 20% ~ 130% and the principal strain turns because of the gap between bearing and slide in the loading range of 0% ~ 20%. The experimental results show that high energy stress conditions of trailing edge flaps and the servo effect of the system are satisfactory, and the method has vital engineering application value for aircraft with high density energy systems.